Baseplates for keyed installation of components in a cargo hold and loading and storage system and associated methods

ABSTRACT

A system for ensuring proper installation of components of a cargo management system within a cargo hold has cleats rigidly attached to a floor of the cargo hold, a first subset of the cleats having insets of a first shape, a second subset of cleats having insets of a second shape, keys and rotatable fasteners attached to the components of the cargo management system, a first subset of the keys having the first shape and a second subset of the keys having the second shape. The first subset of keys can only engage with the first subset of cleats and the second subset of keys can only engage with the second subset of cleats and the rotatable fasteners utilize a rotary movement to secure the components of the cargo management system to a respective cleat, against which the rotary fastener is engaged.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of and claims priority to PCTApplication No. PCT/IB2019/061236, which was filed Dec. 20, 2019, whichclaims the benefit of and priority to U.S. Provisional PatentApplication Ser. No. 62/786,718, which was filed Dec. 31, 2018, U.S.Provisional Patent Application Ser. No. 62/786,736, which was filed Dec.31, 2018, and U.S. Provisional Patent Application Ser. No. 62/786,747,which was filed Dec. 31, 2018, each of which are incorporated herein byreference in their entirety.

TECHNICAL FIELD

The disclosure herein relates to a system for moving loads, inparticular within a cargo hold area of an aircraft, as well as a lockingarrangement and transport vehicle for being used in the system.Moreover, the disclosure herein relates to a method of operating arespective system for moving loads (e.g., cargo containers) within acargo hold area (e.g., of an aircraft).

BACKGROUND

Cargo holds for cargo or passenger aircraft are normally used either forloading with cargo containers or for so-called bulk loading. Such cargocontainers can be standardized containers or standardized pallets,sometimes referred to as Unit Load Devices (ULDs). For moving the ULDswithin the cargo hold, rows of rollers are typically integrated into acargo hold floor of the cargo hold which, depending on their specificdesign, may allow for a direction-dependent or direction-independentmovement of the ULDs. A cargo hold comprising a respective row ofrollers is shown, for example, in EP 1 527 993 B1.

The ULDs can be manually pushed and moved on the row of rollers.Alternatively, an electric drive system comprising Power Drive Units(PDUs) within or next to the row of rollers can be used forautomatically moving the ULDs within the cargo hold.

It is further known to, in addition or as an alternative to possiblePDUs, use transport vehicles for moving the ULDs along the row ofrollers and in parallel to the cargo hold floor. Such transport vehiclesare typically only exerted to reaction and/or inertial forces frommoving the ULDs, whereas the often significantly higher weight forcesare carried by the row of rollers.

When arranging loads, in particular in the form of ULDs, within thecargo hold, it has to be ensured that these are reliably held in placeduring transport. This specifically relates to the cargo hold of anaircraft which experiences large forces and shocks during takeoff andlanding. It is known to use locking arrangements for this purpose, whichmay be floor-mounted or even integrated into the row of rollers. Yet,for activating these locking arrangements, these have to be eithermanually operated or each equipped with individual motors and actuationsystems. The latter alternative further requires cabling to connect themotors to some form of remote control unit. This way, the system'soverall weight and complexity are significantly increased.

For loading with cargo containers, loading with often very bulky andheavy cargo containers is supported by specific components (e.g.,rollers and various latches) that are installed in the hold. Amongstother tasks, these components here support the loading of cargocontainers into the hold and the transport of the cargo containersinside the hold. Such cargo containers may be filled with severalbaggage items or freight of other types. For bulk loading, the hold isloaded in a loose arrangement with the individual baggage items orfreight items of other types to be transported.

Currently known designs for cargo management systems in a cargo hold ofan aircraft are installed as a unitary system that is installed and isnot easily modified without requiring a large investment in terms ofreconfiguring the components of the cargo management system within thecargo hold. As such, a need exists for a cargo management system that isflexible and easily reconfigurable to accommodate a plurality ofdifferently dimensioned cargo containers in a significantly reducedtime, ideally requiring less than four hours of downtime to reduce laborcosts associated with such reconfigurations efforts.

SUMMARY

Although some of the aspects and details described above have beendescribed in relation to the cargo hold component system, these aspectsmay also be implemented accordingly in the hold. Furthermore, thefeatures of the cargo hold component system described should not beregarded as stand-alone features. Rather, all features of the cargo holdcomponent system may be combined with an arbitrary number of otherdescribed features.

According to an example embodiment, a latch for a cargo managementsystem of a cargo hold is provided, the latch comprising: a base plateconfigured for rigid attachment to a surface of the cargo hold; a latchhead attached to the base plate and configured to prevent a movement ofat least one cargo unit in a Y-direction and a Z-direction and to allowa movement of the at least one cargo unit in an X-direction; and aroller assembly attached to the base plate, opposite the latch head, andcomprising at least one roller, the roller being configured to provide avertical support to the at least one cargo unit in the Z-direction whileallowing the movement of the at least one cargo unit in the X-direction.In some such embodiments of the latch, the at least one cargo unit is atleast one unit load device (ULD). In some such embodiments of the latch,the latch head comprises a latch toe formed on an edge thereof, thelatch toe being configured to engage against a base-latch heel formed inthe base plate to secure the latch head within a latch head slot formedin the base plate. In some such embodiments of the latch, the base plateand the latch head comprise corresponding latch-base alignment features,including a protuberance on the base plate and a cavity formed in abottom surface of the latch head, wherein, when the latch toe is engagedagainst the base-latch heel, the latch head is configured to pivotablyrotate into an installed position, in which the protuberance is locatedwithin the cavity. In some such embodiments of the latch, theprotuberance comprises a first through-hole formed through a thicknessthereof, wherein the latch head comprises a second through-hole formedthrough a thickness thereof, wherein the first and second through-holesare substantially coaxial to each other when the cavity covers theprotuberance, and wherein a pull pin is installed through the first andsecond through-holes to rigidly attach the latch head against the baseplate in the installed position. In some such embodiments of the latch,the roller assembly comprises a frame having a roller toe formed on anedge thereof, the roller toe being configured to engage against abase-roller heel formed in the base plate, adjacent the base-latch heel,to secure the roller assembly to the base plate. In some suchembodiments of the latch, the base plate and the roller assemblycomprise corresponding roller-base alignment features, including a ribformed on the base plate and a recess formed in a bottom surface of theroller assembly, wherein, when the roller toe is engaged against thebase-roller heel, the roller assembly is configured to pivotably rotateinto an installed position, in which the rib is located within therecess. In some such embodiments of the latch, the roller-base alignmentfeatures comprise at least two slots formed in opposite sides, relativeto the X-direction, of the base plate and at least two lateral tabsattached to the roller assembly, wherein each lateral tab is configuredto engage within a corresponding slot of the at least two slots when theroller assembly is in the installed position. In some such embodimentsof the latch, when the roller assembly is only partially engaged overthe base plate, the at least two lateral tabs protrude from the rollerbase in the X-direction as a visual indicator of the partial engagementof the roller assembly over the base plate. In some such embodiments ofthe latch, the at least two slots comprise a keyed portion with whichthe corresponding lateral tabs engage to provide a retention force toprevent, along with the roller toe being engaged with the base-rollertoe, separation of the roller assembly from the base plate in theY-direction and/or the Z-direction. In some such embodiments of thelatch, the roller-base alignment features are configured to preventrelative movement between the base plate and the roller assembly in theX-direction.

According to another example embodiment, a method of installing a latchin a cargo management system in a cargo hold is provided, the methodcomprising: attaching a base plate to a surface within the cargo hold;attaching a latch head to the base plate; and attaching a rollerassembly to the base plate. In some such embodiments of the method,attaching the latch head to the base plate comprises: engaging a latchtoe against a base-latch heel of the base plate; pivoting the latch headdown against the base plate into an installed position, such that aprotuberance extending from the base plate towards and/or within acavity of the latch head is covered; and inserting a pull pin through afirst through-hole formed through the protuberance and a secondthrough-hole formed through the latch head, which are substantiallyco-axial when the latch head is in the installed position. In some suchembodiments of the method, pivoting the latch head down against the baseplate into the installed position prevents a movement of the latch headrelative to the base plate in the X-direction and the Y-direction. Insome such embodiments of the method, attaching the roller assembly tothe base plate comprises: engaging a roller toe against a base-rollerheel of the base plate; and pivoting the latch head down against thebase plate, over roller-base alignment features, comprising a rib andslots formed in the base plate and a recess and lateral tabs attachedand/or formed in the roller assembly, such that the lateral tabs arelocated within a slot formed in the base plate. In some such embodimentsof the method, the rib and the recess are defined in a Y-Z plane. Insome such embodiments of the method, the roller-base alignment featuresprevent motion of the roller assembly in at least the X-directionrelative to the base plate. In some such embodiments of the method, theroller assembly allows a motion of a cargo unit through the Y-Z latch ina substantially frictionless manner. In some such embodiments of themethod, the cargo unit is a unit load device (ULD).

According to another embodiment, a system for ensuring properinstallation of components of a cargo management system within a cargohold is disclosed, the system comprising: a plurality of cleats rigidlyattached to a floor of the cargo hold, a first subset of the pluralityof cleats comprising insets having a first shape, a second subset of theplurality of cleats comprising insets having a second shape, keys androtatable fasteners attached to the components of the cargo managementsystem, a first subset of the keys having the first shape and a secondsubset of the keys having the second shape, wherein the first subset ofkeys can only engage with the first subset of cleats and the secondsubset of keys can only engage with the second subset of cleats, andwherein the rotatable fasteners are configured for rotary movement tosecure the components of the cargo management system to a respectivecleat against which the rotary fastener is engaged. In some embodimentsof the system, the first and second shapes are different shapes. In someembodiments of the system, the first and second shapes comprisegeometric or amorphous shapes. In some embodiments of the system, thegeometric shapes comprise one or more of a square, a triangle, a circle,a hexagon, a pentagon, and an hourglass. In some embodiments of thesystem, each of the cleats comprises a back, through which each cleat isrigidly attached to the cargo hold floor, at least two side walls onopposing lateral sides of the back, and a top surface, against which therotatable fasteners are tightened to secure the components of the cargomanagement system to the cleat. In some embodiments of the system, atleast one cleat has at least two insets formed through a thickness ofthe upper surface, into which a corresponding one of the keys can beinserted during installation of the components of the cargo managementsystem. In some embodiments of the system, at least one cleat has a slotformed through a thickness of the upper surface, the slot beingcontinuous and uninterrupted along a length of the cleat to bifurcatethe upper surface of the cleat, thereby defining at least two flanges inthe cleat. In some embodiments of the system, the rotatable fastenersare configured for insertion through the slot and to engage with aninternal surface of the at least two flanges. In some embodiments, thesystem comprises a tightener for each rotatable fastener, wherein thetightener is configured to clamp the flanges between the rotatablefastener and the component of the cargo management system to which thetightener is attached progressively tighter due to a rotary movement ofthe tightener. In some embodiments of the system, a width of therotatable fasteners is less than a distance between the side walls ofthe cleat.

According to another example embodiment, a method of installingcomponents of a cargo management system is disclosed herein, the methodcomprising: forming and/or providing insets having a first shape in anupper surface of a first subset of a plurality of cleats; forming and/orproviding insets having a second shape in an upper surface of a secondsubset of the plurality of cleats; rigidly attaching a plurality ofcleats to a floor of the cargo hold; attaching keys and rotatablefasteners to the components of the cargo management system, a firstsubset of the keys having the first shape and a second subset of thekeys having the second shape; engaging the first subset of keys with thefirst subset of cleats; engaging the second subset of keys with thesecond subset of cleats; and rotating the rotatable fasteners areconfigured to secure the components of the cargo management system to arespective cleat against which the rotary fastener is engaged. In someembodiments of the method, the first and second shapes are differentshapes. In some embodiments of the method, the first and second shapescomprise geometric or amorphous shapes. In some embodiments of themethod, the geometric shapes comprise one or more of a square, atriangle, a circle, a hexagon, a pentagon, and an hourglass. In someembodiments of the method, each cleat comprises a back, through whicheach cleat is rigidly attached to the cargo hold floor, at least twoside walls on opposing lateral sides of the back, and a top surface,against which the rotatable fasteners are tightened to secure thecomponents of the cargo management system to the cleat. In someembodiments of the method, at least one cleat has at least two insetsformed through a thickness of the upper surface, into which acorresponding one of the keys can be inserted during installation of thecomponents of the cargo management system. In some embodiments of themethod, at least one cleat has a slot formed through a thickness of theupper surface, the slot being continuous and uninterrupted along alength of the cleat to bifurcate the upper surface of the cleat, therebydefining at least two flanges in the cleat. In some embodiments, themethod comprises inserting the rotatable fasteners through the slot toengage with an internal surface of the at least two flanges. In someembodiments, the method comprises progressively tightening the flangesbetween the rotatable fastener and the component of the cargo managementsystem to which the tightener is attached by rotating the tightener in afirst direction. In some embodiments of the method, a width of therotatable fasteners is less than a distance between the side walls ofthe cleat.

According to another example embodiment, a power drive unit (PDU) fortransporting cargo units into, out of, and/or within a cargo hold isprovided, the PDU comprising: a frame, by which the PDU is rigidlyattached to a floor of the cargo hold; a body pivotably attached, via ahinge, at a first end of the frame; at least one drive roller attachedat a second end of the body; and an actuator attached to the body andconfigured to cause a pivoting angular movement of the body, relative tothe frame, about the hinge, wherein an angular position of the bodyrelative to the frame is maintained by the actuator even upon a loss ofpower to the PDU, and wherein the body is configured to move between andincluding a retracted position and a deployed position. In someembodiments, the cargo units are unit load devices (ULDs) In someembodiments of the PDU, when the body is in the retracted position, theat least one drive roller is positioned entirely below a plane in whicha bottom surface of the cargo units travels within the cargo hold so asto not be in contact with the cargo units and, when the body is in thedeployed position, the at least one drive roller is positioned such thatat least a portion thereof extends coincident to or beyond the plane inwhich the bottom surface of the cargo units travels within the cargohold so that the at least one drive roller contacts the cargo units asthe cargo units are transported within the cargo hold. In someembodiments of the PDU, the actuator comprises at least one rollerhaving an eccentric shape. In some embodiments of the PDU, the eccentricshape is a substantially ovular shape having a first diameter and asecond diameter, the first diameter being different from the seconddiameter. In some embodiments of the PDU, the first diameter has a sizethat is smaller than a distance measured from an axis of rotation of theactuator to a bottom surface of the body and the second diameter has asize that is larger than the distance measured from the axis of rotationof the actuator to the bottom surface of the body. In some embodimentsof the PDU, an angular velocity of the body relative to the frameincreases as the body moves from the retracted position to the deployedposition. In some embodiments of the PDU, an angular velocity of thebody relative to the frame decreases as the body moves from the deployedposition to the retracted position. In some embodiments, the PDUcomprises a direct current (DC) brushless motor to reduce or eliminateinrush current and enable transport speed management of cargo unitswithin the cargo hold.

According to another example embodiment, a cargo management systemcomprising a plurality of the PDUs described hereinabove is disclosed,at least one of the plurality of PDUs comprising a controlled areanetwork (CAN) bus interface to control and communicate with acontroller. In some embodiments of the cargo management system, thecargo units are unit load devices (ULDs). In some embodiments of thecargo management system, the at least one PDU is configured to providepredictive maintenance information, including roller health monitoring,operational cycles, and power events of the at least one PDU. In someembodiments, the cargo management system comprises at least oneproximity or position sensor adjacent the at least one PDU to detect alatched cargo unit in a stationary position over the PDU. In someembodiments of the cargo management system, the at least one PDU isconfigured for PIN programming via two PINs at a connector by providingdifferent resistance values thereto. In some embodiments of the cargomanagement system, the at least one PDU is configured to providemaintenance and operational data via the CAN bus. In some embodiments ofthe cargo management system, the at least one PDU comprises at leastfirst and second PDUs, the first PDU being installed within the cargohold in a ball mat area, adjacent a cargo hold door, to transport acargo unit in a transverse direction of the cargo hold and the secondPDU being installed within the cargo hold in the ball mat area totransport a cargo unit in a longitudinal direction of the cargo hold. Insome embodiments of the cargo management system, when one or more of thecargo units is being transported in the transverse direction, the bodyof the first PDU is in the deployed position and the body of the secondPDU is in the retracted position. In some embodiments of the cargomanagement system, when one or more of the cargo units is beingtransported in the longitudinal direction, the body of the first PDU isin the retracted position and the body of the second PDU is in thedeployed position. In some embodiments of the cargo management system,when cargo units are loaded within the cargo hold, the body of the firstPDU is moved into or maintained in the deployed position to provideanti-roll-out functionality to a cargo unit within the cargo hold in theball mat area adjacent the cargo hold door.

According to another example embodiment, a method of transporting cargounits into, out of, and/or within a cargo hold using at least one powerdrive unit (PDU) is provided, the method comprising: rigidly attaching aframe of the at least one PDU a floor of the cargo hold; pivotablyattaching a body of the at least one PDU, via a hinge, at a first end ofthe frame; attaching at least one drive roller at a second end of thebody; driving a pivoting angular movement of the body, relative to theframe, about the hinge using an actuator attached to the body, theangular movement of the body being between and including a retractedposition and a deployed position; and maintaining, upon a loss of powerto the at least one PDU, an angular position of the body relative to theframe. In some embodiments of the method, the cargo units are unit loaddevices (ULDs). In some embodiments of the method, when the body is inthe retracted position, the at least one drive roller is positionedentirely below a plane in which a bottom surface of the cargo unitstravels within the cargo hold so as to not be in contact with the cargounits and, when the body is in the deployed position, the at least onedrive roller is positioned such that at least a portion thereof extendscoincident to or beyond the plane in which the bottom surface of thecargo units travels within the cargo hold so that the at least one driveroller contacts the cargo units as the cargo units are transportedwithin the cargo hold. In some embodiments of the method, the actuatorcomprises at least one roller having an eccentric shape. In someembodiments of the method, the eccentric shape is a substantially ovularshape having a first diameter and a second diameter, the first diameterbeing different from the second diameter. In some embodiments of themethod, the first diameter has a size that is smaller than a distancemeasured from an axis of rotation of the actuator to a bottom surface ofthe body and the second diameter has a size that is larger than thedistance measured from the axis of rotation of the actuator to thebottom surface of the body. In some embodiments of the method, anangular velocity of the body relative to the frame increases as the bodymoves from the retracted position to the deployed position. In someembodiments of the method, an angular velocity of the body relative tothe frame decreases as the body moves from the deployed position to theretracted position. In some embodiments of the method, the at least onePDU comprises a direct current (DC) brushless motor to reduce oreliminate inrush current and enable transport speed management of cargounits within the cargo hold. In some embodiments, the method comprisescontrolling the at least one PDU and communicating with a controller viaa controlled area network (CAN) bus interface. In some embodiments, themethod comprises providing predictive maintenance information, includingroller health monitoring, operational cycles, and power events of the atleast one PDU to the controller via the CAN bus. In some embodiments,the method comprises detecting, via at least one proximity or positionsensor adjacent the at least one PDU, a latched cargo unit in astationary position over the PDU. In some embodiments, the methodcomprises PIN programming the at least one PDU via two PINs at aconnector by providing different resistance values thereto. In someembodiments, the method comprises providing maintenance and operationaldata regarding the at least one PDU via the CAN bus. In some embodimentsof the method, the at least one PDU comprises at least first and secondPDUs, the method comprising transporting, using the first PDU, which isinstalled within the cargo hold in a ball mat area, adjacent a cargohold door, a cargo unit in a transverse direction of the cargo hold andtransporting, using the second PDU, which is installed within the cargohold in the ball mat area, a cargo unit in a longitudinal direction ofthe cargo hold. In some embodiments of the method, when a cargo unit isbeing transported in the transverse direction, the body of the first PDUis in the deployed position and the body of the second PDU is in theretracted position. In some embodiments of the method, when a cargo unitis being transported in the longitudinal direction, the body of thefirst PDU is in the retracted position and the body of the second PDU isin the deployed position. In some embodiments, the method comprises,when all cargo units are loaded within the cargo hold, moving ormaintaining the body of the first PDU into the deployed position toprovide anti-roll-out functionality to a cargo unit within the cargohold in the ball mat area adjacent the cargo hold door.

Further features, properties, advantages and possible derivations willbe evident to the person skilled in the art from the description belowwhich refers to the attached, example drawings. All features describedand/or depicted in the drawings, alone or in arbitrary combinations,indicate the object disclosed herein. The dimensions and proportions ofthe components shown in the figures are not to scale.

BRIEF DESCRIPTION OF THE DRAWINGS

The disclosure herein will be explained in more detail with reference tofigures. The example figures referenced below illustrate schematically:

FIG. 1 is a schematic top view of the points of ingress and egress of anaircraft for passengers, crew, cargo, and the like;

FIG. 2 is an example schematic side view of an aircraft having aplurality of cargo holds;

FIG. 3 is an example schematic view of a fore cargo hold shown in theaircraft of FIG. 2;

FIGS. 4 and 5 are example schematic views of the aft cargo holds shownin the aircraft of FIG. 2;

FIG. 6 is an image of an example image of a cargo hold in an aircraftconfigured as a cargo aircraft;

FIG. 7 is an example schematic view of a cargo aircraft configured toreceive one or more ULDs within its cargo hold;

FIG. 8 is an example top view of an embodiment of a cargo floor within acargo hold of an aircraft;

FIG. 9 is an example schematic view of a cargo aircraft configured toreceive one or more ULDs within its cargo hold;

FIG. 10 is an isolated schematic view of a cargo hold from the aircraftshown in FIG. 9, the cargo hold being configured to receive one or moreULDs therein;

FIG. 11 is an example embodiment of a cargo hold configured to receivecargo containers in the form of ULDs;

FIG. 12 is another view of the example embodiment of the cargo hold fromFIG. 11;

FIG. 13 is a detailed view of components of the cargo management systeminstalled along a main drive rail within the cargo hold of FIGS. 11 and12;

FIG. 14 is an exploded view of FIG. 13, showing the attachment cleatsused to removably secure the components of the cargo management systemalong the main drive rail;

FIG. 15 is an example view showing a power drive unit (PDU) installed ata designated position along the main drive rail;

FIG. 16A is a schematic illustration of an example embodiment of abi-stable PDU in a retracted position;

FIG. 16B is a schematic illustration of the bi-stable PDU of FIG. 16A ina deployed position;

FIG. 17 is an example schematic illustration of PDUs arranged in a cargohold to provide transverse and longitudinal movement of ULDs therein;

FIG. 18 is an exploded view of the PDU spaced apart from the main driverail to show the attachment cleats used to removably secure thecomponents of the cargo management system along the main drive rail toensure a desired orientation of such components is maintained;

FIG. 19 is another exploded view of the PDU shown in FIG. 13 spacedapart from the main drive rail to show the keyed engagement featuresthat are attached to the underside of the frame of the components of thecargo management system, the keyed engagement features being provided tofit only within compatible attachment cleats;

FIG. 20A shows keyed engagement features in the shape of a square androtatable fasteners on the underside of the frame of a roller assembly,the keyed engagement features and rotatable fasteners being arranged tofit within and engage with the square-shaped recessed insets in thesquare cleat shown in FIG. 20B;

FIG. 21 shows an attachment cleat with triangle-shaped insets, intowhich corresponding keyed engagement features attached to a component ofa cargo management system can be inserted to secure such a componentwithin a cargo hold of an aircraft;

FIG. 22A shows keyed engagement features in the shape of a circle androtatable fasteners on the underside of a frame of a PDU, the keyedengagement features and rotatable fasteners being arranged to fit withinand engage with a circle-shaped recessed insets in the correspondingcircle cleat shown in FIG. 22B;

FIG. 23A shows keyed engagement features generally in the shape of anhourglass and rotatable fasteners on the underside of the frame of aroller assembly, the keyed engagement features and rotatable fastenersbeing arranged to fit within and engage with the hourglass-shapedrecessed insets in the corresponding hourglass cleat shown in FIG. 23B;

FIGS. 24A through 24D show example shapes suitable for use as therecessed insets of an attachment cleat and the keyed engagement featuresattached to a component of a cargo management system;

FIG. 25 is an isolated view of a Y-Z latch installed within the cargohold of FIGS. 11 and 12, the Y-Z latch being for restraining movement ofcargo engaged therewith in the Y- and Z-directions;

FIG. 26 is a side view of the Y-Z latch shown in FIG. 25;

FIG. 27 is a top view of the Y-Z latch shown in FIG. 25;

FIG. 28 is an exploded view of the Y-Z latch shown in FIG. 25;

FIG. 29 is an isolated view of the Y-Z latch shown in FIG. 25 in analternative configuration;

FIG. 30 is an exploded view of the Y-Z latch shown in FIG. 29; and

FIGS. 31A and 31B show installation motions of the constituentcomponents of the Y-Z latch shown in FIG. 25.

DETAILED DESCRIPTION

In the description below, without being restricted hereto, specificdetails are presented in order to give a complete understanding of thedisclosure herein. It is, however, clear to a person skilled in the artthat the disclosure herein may be used in other example embodimentswhich may differ from the details outlined below. The figures servefurthermore merely to illustrate example embodiments, are not to scale,and serve merely to illustrate by example the general concept of thedisclosure herein. For example, features contained in the figures mustnot necessarily be considered to be essential components.

Comparable or identical components and features, or those with similareffect, carry the same reference signs in the figures. For reasons ofclarity, in the figures sometimes the reference signs of individualfeatures and components have been omitted, wherein these features andcomponents carry reference signs in the other figures.

FIG. 1 is a schematic top view of the points of ingress and egress of anaircraft, generally designated 10, for passengers, crew, cargo, and thelike while the aircraft 10 is on the ground (e.g., at an airportterminal being resupplied during an aircraft turnaround between flightsof the aircraft 10). The aircraft 10 is shown being connected to aplurality of example ground support units and systems. One or more cargoloaders, generally designated 24, can be placed next to the fuselage ofthe aircraft 10 to load cargo into the cargo hold of the aircraft 10,either manually or in an automated manner. In some embodiments, one ormore (e.g., all) of the cargo loaders 24 can be bulk loaders and/orhighlifters. In general, one cargo loader 24 will be provided at anentry door to each segregated and/or partitioned portion of a cargo holdin an aircraft 10 where the cargo hold is not continuous along thelength of the aircraft 10.

A passenger loading bridge and/or stairway, generally designated 22, isused to allow passengers to walk from an airport terminal onto theaircraft 10. Galley service vehicle, generally designated 26, can bearranged at the fore and/or aft of the aircraft 10 to resupply thegalleys of the aircraft 10. A water service vehicle, generallydesignated 28, can be connected to the aircraft 10 to remove waterconsumed during a previous flight and to supply fresh water for use bythe passengers and/or crew of the aircraft 10 during a subsequentflight. A lavatory service vehicle, generally designated 30, isconnected to remove wastewater generated by use of the lavatory of theaircraft 10. A stairway, generally designated 32, may be connected atone or more cabin doors of the aircraft 10 for loading people and/oritems from a tarmac of the airport. The aircraft 10 is connected to anelectrical ground power unit, generally designated 34, which suppliespower to the aircraft 10 while, e.g., the engines of the aircraft 10 arepowered down and/or disengaged. An air starting unit or air conditioningvehicle, generally designated 36 is connected to the aircraft to provideconditioned air to the interior of the aircraft for passenger and crewcomfort while the aircraft 10 is on the ground with the aircraft enginesand associated passenger/crew comfort systems turned off and/ordisengaged.

FIG. 2 is a side view of an example aircraft, generally designated 10,having at least one fore cargo hold, generally designated 40, andprimary and auxiliary aft cargo holds, generally designated 50, 50A,respectively.

FIG. 3 shows an example embodiment of a fore cargo hold 40 which hasbeen segmented, whether virtually, through use of attachment componentsto secure cargo only at particular locations within the fore cargo hold40, and/or by physical partitions and/or segmentation of the fore cargohold 40. As shown, the fore cargo hold 40 is subdivided into a firstfore cargo area, generally designated 41, a second fore cargo area,generally designated 42, and a third fore cargo area, generallydesignated 43. In general, it is advantageous for any such physicalpartitions and/or segmentation within the fore cargo hold 40 to beremovable and/or configurable (e.g., not fixed in place) to allow formovement of cargo loaded at one end of the fore cargo hold 40, e.g., infirst fore cargo area 41, to be moved into another cargo area within thefore cargo hold 40, whether the second fore cargo area 42 or the thirdfore cargo area 43. The fore cargo hold 40 may be subdivided into anydesirable number and size areas (e.g., a plurality of such areas) as isdesired based on the cargo configuration that the aircraft is intendedto transport.

FIG. 4 shows an example embodiment of a primary aft cargo hold 50 whichhas been segmented, whether virtually, through use of attachmentcomponents to secure cargo only at particular locations within theprimary aft cargo hold 50, and/or by physical partitions and/orsegmentation of the primary aft cargo hold 50. As shown, the primary aftcargo hold 50 is subdivided into a first primary aft cargo area,generally designated 51, a second primary aft cargo area, generallydesignated 52, a third primary aft cargo area, generally designated 53,and a fourth primary aft cargo area, generally designated 54. Ingeneral, it is advantageous for any such physical partitions and/orsegmentation within the primary aft cargo hold 50 to be removable and/orconfigurable (e.g., not fixed in place) to allow for movement of cargoloaded at one end of the primary aft cargo hold 50, e.g., in firstprimary aft cargo area 51, to be moved into another cargo area withinthe primary aft cargo hold 50, whether the second primary aft cargo area52, the third primary aft cargo area 53, or the fourth primary aft cargoarea 54. The primary aft cargo hold 50 may be subdivided into anydesirable number and size areas (e.g., a plurality of such areas) as isdesired based on the cargo configuration that the aircraft is intendedto transport.

FIG. 5 shows an example embodiment of an auxiliary aft cargo hold 50A,which can be physically segregated from, and have a separate loadingdoor from, the primary aft cargo hold 50, and/or which can be physicallyconnected and segregated, either virtually, as described elsewhereherein, or physically with a barrier, which can be permanent or,advantageously, removable. In the embodiment show, the auxiliary aftcargo hold 50A has only a single auxiliary aft cargo area, generallydesignated 55, but may be subdivided into any desirable number and sizeareas (e.g., a plurality of such areas) as is desired based on the cargoconfiguration that the aircraft is intended to transport.

FIG. 6 is an interior illustration of an example embodiment of anaircraft cargo hold 40E configured as a cargo aircraft (see 10C, FIG.7), having roller assemblies, generally designated 200, power driveunits (PDUs), generally designated 100, X-Z latches, generallydesignated 300, and Y-Z latches, generally designated 400, arrangedalong the length of the cargo hold 40E and one or more ball mats 60installed on the cargo floor 4 of the cargo hold 40E. There may be aplurality of ball mats 60, but regardless of the number, the ball mats60 allow for multi-dimensional motion of the cargo units, which areshown in FIGS. 7-10 as unit load devices (ULDs), but which may be anytype of cargo unit, including, for example, palletized freight, at theentry of the cargo hold 40E adjacent the door through which cargo isloaded and unloaded from the cargo hold 40E. FIG. 7 is an exteriorschematic view of the example cargo aircraft, generally designated 10C,of FIG. 6, in which the cargo aircraft 10C has only a minimal or nopassenger area, the majority of the interior space of the cargo aircraft10C. In the embodiment shown, the cargo hold 40E is accessed through acargo door 11, by which a cargo unit 1 is loaded onto the aircraft via aloading ramp 12. FIG. 8 schematically shows an example embodiment of aportion of a cargo hold 40E, showing the roller assemblies 200, PDUs100, and ball mat 60 arranged at the entrance of the cargo hold 40E ofsuch a cargo aircraft as is shown in FIGS. 6 and 7. The cargo unit 1 isloaded via the loading ramp 12 onto the ball mat 60 and can then bedriven in either direction along the longitudinal axis of the aircraft,the direction being generally designated T, such that the cargo unit 1can be moved in the fore or aft direction within the cargo hold 40E.FIGS. 9 and 10 schematically show another example embodiment of apassenger aircraft 10 with a fore cargo hold 40 located underneath thepassenger cabin 14 and in front of the wing 15 of the aircraft. A cargoloader 24 is provided to load the cargo units 1 into the fore cargo hold40 through the cargo door 11, then the cargo units 1 are moved along thelength of the fore cargo hold 40 to a position designated so that all ofthe cargo units 1 can be loaded into the fore cargo hold 40.

FIGS. 11 and 12 show another example embodiment of a cargo hold 40, 50,50A, that has a floor 4 and is accessible through a cargo door 11. Whilethe example embodiment shown is a cargo hold underneath a passengercabin of an aircraft, the foregoing descriptions apply equally in acargo hold (e.g., 40E, FIGS. 6 and 7) of a cargo aircraft (e.g., 10C,FIG. 7). Adjacent the cargo door 11, a plurality of ball mats 60 areinstalled in and/or on the floor 4 of the cargo hold 40, 50, 50A. A maindrive rail 6 is arranged along all or at least a portion of (e.g., amajority of) the length of the cargo hold 40, 50, 50A. PDUs, generallydesignated 100, roller assemblies, generally designated 200, and/or X-Zlatches, generally designated 300, are arranged along the main driverail 6. In some embodiments, the cargo hold 40, 50, 50A may have aplurality of substantially parallel main drive rails 6, the term“substantially parallel” meaning that the main drive rails 6 areparallel to each other within a tolerance of the construction methodsused in the construction of the cargo hold 40, 50, 50A. The PDUs 100and/or X-Z latches 300 can be installed within the area where the ballmat(s) 60 are located. The PDUS 100 are configured to move the cargo(e.g., the cargo units 1, see FIGS. 9 and 10) along the length of thecargo hold 40, 50, 50A. The Y-Z latches, generally designated 400, arelocated along the lateral edges of the floor 4 of the cargo hold 40, 50,50A so as to not block movement of the cargo along the length of thecargo hold 40, 50, 50A to and/or from a designated stowage position. TheY-Z latches 400 are therefore arranged at preset intervals and spacedapart from each other along the longitudinal axis of the aircraft. EachX-Z latch 300 can be spring-loaded and actuatable to prevent motion ofthe cargo against which the X-Z latch 300 is engaged in the X-direction(e.g., along the length of the aircraft) and the Z-direction (e.g., thevertical direction).

FIG. 13 shows an example embodiment of a main drive rail 6 installed ina cargo hold, such as is shown in FIGS. 11 and 12, with a plurality ofPDUs 100, roller assemblies 200, X-Z latches 300, Y-Z latches 400, andthe like attached thereto in a designated configuration to facilitatemovement and retention of cargo units (see, e.g., 1 in FIGS. 9 and 10)within the cargo hold in which the main drive rail 6 is installed. Themain drive rail 6 can extend up to, or into, the ball mat (60, see FIGS.11 and 12) or other suitable analogue located adjacent the entry to thecargo hold (e.g., at the cargo door 11), and is configured to transportULDs, once they are loaded within the cargo hold, to a designatedposition within the cargo hold for transport to a destination by theaircraft. The roller assemblies 200 are configured to allow forsubstantially frictionless, at least compared to a sliding surfaceinterface, movement of cargo along the length of the cargo hold, but areidler rollers, meaning that the rollers of the roller assemblies 200 arenot driven, however, in some embodiments, one or more of the rollers ofone or more of the roller assemblies 200 can be driven, rather thanidler, rollers.

The PDUs 100 are configured with a one or a plurality of driven rollers140 that engages against a surface (e.g., a bottom surface) of the cargoto move the cargo by a frictional rotation of the driven roller 140against the cargo. The Y-Z latches 400 are typically installed about theperimeter of the cargo hold and configured to engage with a laterallyextending flange of the cargo unit (e.g., of the ULD) passing throughthe cargo hold to prevent relative movement of the cargo within thecargo hold in the Y- and Z-directions. The X-Z latches 300 are typicallyinstalled along the main drive rail 6 at a designated spacing (e.g.,pitch) based on the length of the ULDs (e.g., as measured in theX-direction) and are configured to engage with a flange of the cargounit about which the latch is engaged to prevent relative movement ofthe cargo unit within the cargo hold in the X- and Z-directions. The X-Zlatches 300 are typically spring-loaded and movable between andincluding deployed and retracted positions. In the retracted positions,the components of the X-Z latch are all located beneath the plane inwhich the cargo unit travels (e.g., beneath the top surface of theroller assemblies 200 and/or PDUs 100) so that the cargo units can passover the X-Z latches 300 without any physical contact occurring betweenthe cargo units and the X-Z latches 300. In the deployed positions, theX-Z latches have a generally hooked shape (e.g., in the shape of aninverted L) that engage over (e.g., in the Z-direction) and against(e.g., in the X-direction) the flange of the cargo unit to preventfurther movement of the cargo unit in the X- and Z-directions beyond thesurfaces of the X-Z latch 300 where it contacts the flange of the cargounit.

FIG. 14 is a partially exploded view of the main drive rail 6 shown inFIG. 13, showing the PDUs 100, roller assemblies 200, and X-Z latches300 spaced vertically away from the main drive rail 6, thereby showingthe attachment cleats 500, 510, 520 used to define which of the PDUs100, roller assemblies 200, and X-Z latches 300 can be installed basedon an installation pattern of the cleats 500, 510, and 520 on the maindrive rail 6. Each cleat 500, 510, and 520 has, as viewedcross-sectionally along the X-direction, a generally C-shape with a backportion attached to the cargo hold floor 4 at designated positions, sidewalls extending away from the lateral edges of the back portion in theZ-direction, perpendicular to the X-Y plane defining the cargo holdfloor 4, and flanges that are spaced vertically apart from, butsubstantially parallel to, the cargo hold floor 4 and the back portionof the cleat 500, 510, and 520. In some embodiments, the flanges areseparated by a slot that is uninterrupted along the length of the cleat500, 510, and 520. In some embodiments, the flanges are in the form of aunitary top surface with inset shapes formed through a thickness (e.g.,in the Z-direction) of the cleat 500, 510, and 520. These insets can beformed in any shape, including, for example, circle, triangle, square,and hourglass, as shown in FIGS. 24A-24D. Other examples can includepentagons, hexagons, or any shape, including non-geometric shapes. Otheramorphous shapes are contemplated and envisioned in accordance with thedisclosure herein as well.

FIG. 15 is a schematic illustration of an example embodiment of a PDU,generally designated 100, having a base 110 that is connectable to themain drive rail 6 within the cargo hold, a body 120 that is connected tothe base at a pivoting connection point 130, and one or more (e.g., aplurality of) drive rollers 140 that are rotatably driven (e.g., ondemand) about an axis. The body 120 of a PDU 100 is typicallyspring-loaded to be biased in the vertical direction, away from thecargo hold floor 4, to ensure proper engagement of the drive roller(s)140 against the bottom surface of the cargo unit being transportedwithin the cargo hold. The PDU 100 is configured to rotate the driveroller(s) 140 in either direction to facilitate movement of the cargounits in both directions relative to the longitudinal orientation of thePDU 100, thereby enabling both loading and unloading of the cargo unitsinto and out of the cargo hold of the aircraft.

In the example embodiment of the PDU 100 shown in FIGS. 16A and 16B, thePDU 100 has a DC brushless motor, controlled area network (CAN) businterface, speed control management, bi-stable roller positioning, andpredictive maintenance data collection. Such PDUs 100 can be used as areplacement for the door sill latches previously implemented to provideanti-roll-out functionality. As shown, the PDU 100 of FIGS. 16A and 16Bhas, to enable the bi-stable functionality, an integratedeccentrically-shaped actuator 160 (e.g., a roller) that can becontrolled between at least two angular positions. Due to the eccentricshape of the actuator 160, which has a substantially ovular shape, theangular position of the body 120, relative to the base 110 and the cargohold floor 4, can be changed merely by a rotational movement of theactuator 160. The actuator 160 can be a single roller, a plurality ofrollers, one or more wheels, or any combination thereof or of anycomponents capable of operating in such a manner.

In the embodiment shown, a first diameter D1 of the actuator 160 has asize such that it does not extend beyond the lower edge of the body 120of the PDU 100 when the actuator 160 is in the first (e.g., retracted)position shown in FIG. 16A, such that the drive roller 140 is in aposition beneath a plane in which the bottom surface of the cargo unitstravels, so that the drive roller 140 is not in contact with the cargounits when the first diameter D1 of the actuator is perpendicular to thecargo hold floor 4, as shown in FIG. 16A. Due to its eccentric shape,the actuator 160 has a second diameter D2 that is larger than a distancefrom the axis of rotation of the actuator 160 to the bottom surface/edgeof the body 120 of the PDU 100, such that the body 120 is moved into anon-zero angular position relative to the cargo hold floor 4 when thesecond diameter D2 is oriented perpendicularly to the cargo hold floor4, as shown in FIG. 16B. In the deployed position, when the drive roller140 is in contact with the cargo unit, the PDU 100 is able to control amovement (and rate of movement) of the cargo unit with which it is incontact; thus, the PDU 100 is capable of holding, stopping, ortransporting a cargo unit within the cargo hold. Such holdingfunctionality causes the PDU 100 to actively resist movement of thecargo unit from the position in which it is being held by preventingangular movement of the drive roller 140. Such stopping functionalitybrings the cargo unit to a stop (e.g., having zero velocity relative tothe cargo hold in which it is located) but may not actively resistfurther movement of the cargo unit. Such transporting functionalitycauses a movement of the cargo unit within the cargo hold. It is furthercontemplated that the PDU 100 may be only partially deployed in someinstances by only a partial rotation of the actuator 160 of less than90° from the position in which the first diameter D1 is perpendicular tothe cargo hold floor 4. In case of power loss, the drive roller 140 willremain safe in the last position (e.g., retracted or deployed, meaningthat the actuator 160 will not return to a “home” or “rest” position).The drive roller 140, when in the deployed position, therefore providesa braking force to hold the cargo unit even during a power lossscenario, but the cargo unit may be manually moved (e.g., pushed orpulled) over the PDU 100 in such scenarios.

The eccentric shape provides a smooth motion profile to the movement ofthe drive roller 140, relative to the cargo hold floor 4. When movingfrom the retracted position of FIG. 16A into the deployed position ofFIG. 16B, the initial rotary movement of the actuator 160 initiallyproduces a rate of travel of the drive roller 140 away from the cargohold floor 4 that increases as the actuator 160 is progressively turned(e.g., assuming a constant angular velocity). Thus, a vertical velocityof the drive roller 140 from the retracted position to the deployedposition increases, assuming the angular velocity of the actuator 160remains constant, as the position of the drive roller 140 movesprogressively further away from the retracted position. Similarly, whenmoving the drive roller 140 from the deployed position shown in FIG. 16Binto the retracted position shown in FIG. 16A, the initial rotarymovement of the actuator 160 initially produces a rate of travel of thedrive roller 140 towards the cargo hold floor 4 that decreases as theactuator 160 is progressively turned. Thus, a vertical velocity of thedrive roller 140 from the deployed position to the retracted positiondecreases, assuming the angular velocity of the actuator 160 remainsconstant, as the position of the drive roller 140 moves progressivelycloser to the retracted position.

In some embodiments, the PDU 100 is configured to perform predictivemaintenance, for example, by detecting the condition of the material(e.g., rubber) of the drive roller 140 for roller health monitoring,operational cycles, and power events. Furthermore, one or more (e.g., aplurality of) proximity or position sensors 170A, 170B may be providedin or adjacent to the PDU 100 (e.g., fore and/or aft thereof) to detecta latched cargo unit in a position over, at least partially, the PDU100. The PDU 100 is further configured for PIN programming via two PINsat a connector by providing different resistance values (e.g., bycontrolling a value of a variable resistor). A CAN bus interface can beprovided to control the operation of the PDU 100 (e.g., the angularposition of the actuator 160 and the angular velocity of the driveroller 140) and enable communication of the PDU 100 with a cargomanagement system control unit (e.g., a controller). In such embodimentsutilizing a CAN bus interface, the PDU 100 is configured to sendmaintenance and operational data via the CAN bus. In some embodiments,the PDU 100 is configured to have a DC brushless motor to drive theactuator 160 and/or the drive roller 140 to reduce (e.g., eliminate)inrush current and enable transport speed management of the cargo unitswithin the cargo hold by controlling the angular speed of the driveroller(s) 140.

An example system for transporting cargo units (e.g., ULDs) inside aCargo Compartment is shown in FIG. 17, the system comprising a pluralityof PDUs (e.g., including first PDU 100A, second PDU 1008, and third PDU100C) are used. In the area of the ball mat(s) 60, first PDU 100A isused for moving cargo units in a direction transverse to the fore/aftdirection of the aircraft, this transverse direction being marked“IN/OUT”, and the second PDU 100B is used for moving cargo units in thefore/aft direction, which is marked “FWD/AFT”. In the area of the ballmat(s) 60, for the transport of cargo units in the transverse direction,the drive roller of first PDU 100A has to be in the deployed positionshown in FIG. 16B and the drive roller of the second PDU 100B has to bein the retracted position shown in FIG. 16A. In the area of the ballmat(s) 60, for the transport of cargo units in the fore/aft direction,the drive roller of first PDU 100A has to be in the retracted positionand the drive roller of the second PDU 100B has to be in the deployedposition. In the embodiment shown, if no command is given, transversedirection first PDU 100A will be commanded into the deployed position toprovide the Anti-Roll-Out functionality that can be used in the place ofcargo sill latches. In case of power loss or power shut off, the driveroller of each of the PDUs 100A, 100B, 100C will remain in their currentrespective positions, either in the deployed or retracted positions. Tobring the drive roller from the retracted position to the deployedposition and, conversely, from the deployed position to the retractedposition, the PDUs 100A, 100B, 100C are equipped with an actuator 160,such as an excenter. In some embodiments, the PDUs 100A, 100B, 100C havea mechanical override function to bring the drive roller to theretracted position to be able to unload cargo units from the cargo holdin case of a loss of power. This feature is advantageous because, atpresent, all “Single Aisle” PDUs (e.g., in cargo holds having only amain drive rail) are raised based on a joystick drive command in thetransverse or longitudinal directions. Accordingly, when a loss of poweroccurs, these PDUs 100A, 1008, 100C are lowered automatically into theretracted position and do not remain in the deployed position.

Referring to FIG. 14, different cleats 500, 510, 520, 530 (e.g., thosehaving differently shaped insets) can be used to ensure a properorientation of a component, such as a PDU 100, such that the PDU 100 isnot installed backwards, which may result in a reverse movement of thecargo unit within the cargo hold from that intended in suchmisconfigurations. As shown in FIGS. 15 and 18, a pair of circle cleats500 is installed at a first position, spaced apart in the Y-direction,of the main drive rail 6 and a pair of square cleats 510 is installed ata second position, also spaced apart in the Y-direction, of the maindrive rail 6. The specific shapes of the insets of the cleats used isgenerally immaterial and may be any combination, so long as they are“keyed” to only allow installation of the specified component of thecargo management system in only one orientation. Other components havingno preferred directionality, such as the roller assemblies 200, may bemounted using cleats, such as square cleats 510 in FIG. 14 that are thesame or different from each other at the respective opposing ends of theroller assembly, because there is no directionality needed to ensureproper functioning of such components.

Fasteners 700 (e.g., threadable rotary tightening members, such asscrews, nuts, and the like) are provided on each component (e.g., PDUs100, roller assemblies 200, X-Z latches 300, and the like) in a positionaccessible from the top surface of the components being installed,extending through a thickness thereof to a position in which rotatablefasteners 700 become rigidly (e.g., removably) engaged with the flanges506 of the cleats 500, 510, 520, 530, thereby allowing the component tobe tightened securely in the designated position to allow safe andreliable operation of the cargo management system. FIG. 19 shows abottom view of an example PDU 100 having square keys 610 at the cornersof a first end thereof and circle keys 600 at the corners of a secondend thereof. The rotatable fasteners 700 can take any shape, but in theembodiment shown have that of an inverted “T” shape, extendingvertically through the slot 508 and beneath the flanges 506 of therespective cleat 500, 510, 520, 530 to allow rotary movement of therotatable fastener 700 without striking the cleat 500, 510, 520, 530itself and also allowing engagement of the rotatable fastener 700beneath the flanges 506 of the cleat 500, 510, 520, 530 for retention ofthe component thereto. In some embodiments, the rotary fastener 700 mayhave a length (e.g., a distance between ends of the “T” shape) that isgreater than a width between the side walls 504 of the cleat, such thatthe rotatable fastener 700 cannot turn more than ±90° within the cleat500, 510, 520, 530 without contacting one or both of the side walls 504,thereby allowing the rotary fastener 700 to be progressively turned totighten (e.g., squeeze, as by a spring) the flanges 506 of the cleat500, 510, 520, 530 between the rotatable fastener 700 and the bottomside of the frame of the component being attached thereto, thus securingthe component to the cleat 500, 510, 520, 530 in a designatedconfiguration. As such, it is advantageous for the keyed feature (e.g.,600, 610, 620), regardless of the shape, to have a thickness that isless than or, preferably, a same thickness as, that of the flanges 506of the cleat 500, 510, 520, 530 against which it is engaged so that arotary movement of the rotatable fastener 700 is not impeded by thekeyed feature itself.

FIG. 20A shows square keys 610 and rotatable fasteners 700 on theunderside of a roller assembly 200. The square keys 610 and rotatablefasteners 700 are configured to engage with the flanges 506 and squareinsets 515 (see also, FIG. 24B) of a square cleat 510, an exampleembodiment of which is shown in FIG. 20B. The square cleat 500 has abase 502 with mounting hole(s) 503 formed through a thickness of thebase 502 to secure the square cleat 510 to the cargo hold floor 4 usingfasteners passing through the mounting hole(s) 503. The square cleat 510has side walls 504 extending away from the base 502 out of the X-Y planeand connecting with flanges 506, the height of the side walls 504defining a thickness of the slot 508 oriented along the length of thesquare cleat 510 in the X-direction. The flanges 506 and the slot 508are shaped to form square insets 515 that are configured to ensureproper alignment of, and engagement with, a component having square keys(e.g., 610, FIG. 20A) on a bottom surface thereof. The slot 508 iscontinuous and uninterrupted along the length of the square cleat 510.The square cleat 510 has two mounting holes 503 formed in the base 502for fasteners (e.g., bolts, screws, rivets, and the like) to passthrough to rigidly secure the square cleat 510 to the cargo hold floor4. Any number of mounting holes 503 and fasteners may be used, inconjunction with pins formed on the back of the square cleat 510 toensure proper alignment with a corresponding hole formed in the cargohold floor 4, to attach and align the cleat 500 along the cargo holdfloor 4 in a designated configuration. FIG. 20A shows the rotatablefasteners 700 in an engaged position, in which the square keys 610 ofthe roller assembly 200 could not be inserted into the square cleat 510,as the rotatable fastener 700 would contact the top surface of theflange 506 of the square cleat 510, thereby preventing passage of therotatable fasteners 700 beyond the flanges 506 and through the slot 508unless the rotatable fastener 700 were to be rotated from theorientation shown to align with the slot 508 of the square cleat 510.

FIG. 21 shows an example embodiment of a triangle cleat 530. Thetriangle cleat 530 has a base 502 with mounting hole(s) 503 formedthrough a thickness of the base 502 to secure the triangle cleat 530 tothe cargo hold floor 4 using fasteners passing through the mountinghole(s) 503. In some embodiments, alignment features may be formed in aback side of the base 502 to aid in installation of the triangle cleat530 to the cargo hold floor 4. The triangle cleat 530 has side walls 504extending away from the base 502 out of the X-Y plane and connectingwith flanges 506, the height of the side walls 504 defining a thicknessof the slot 508 oriented along the length of the triangle cleat 530 inthe X-direction. The flanges 506 and the slot 508 are shaped to formtriangle insets 535 (see also, FIG. 24C) that are configured to ensureproper alignment of, and engagement with, a component having trianglekeys on a bottom surface thereof. The rotary fasteners 700 of acomponent are configured to vertically pass through the slot 508 of thetriangle cleat 530 and be twisted to secure the component to thetriangle cleat 530.

FIG. 22A shows a bottom surface of a PDU 100 having circle keys 600 thatare configured to engage with a circle cleat 500, an example embodimentof which is shown in FIG. 22B. The circle cleat 500 has a base 502 withmounting hole(s) 503 formed through a thickness of the base 502 tosecure the circle cleat 500 to the cargo hold floor 4 using fastenerspassing through the mounting hole(s) 503. In some embodiments, alignmentfeatures may be formed in a back side of the base 502 to aid ininstallation of the circle cleat 500 to the cargo hold floor 4. Thecircle cleat 500 has side walls 504 extending away from the base 502 outof the X-Y plane and connecting with flanges 506, the height of the sidewalls 504 defining a thickness of the slot 508 oriented along the lengthof the circle cleat 500 in the X-direction. The flanges 506 and the slot508 are shaped to form circle insets 505 (see also, FIG. 24A) that areconfigured to ensure proper alignment of, and engagement with, acomponent having circle keys 600 on a bottom surface thereof. The rotaryfasteners 700 of a component are configured to vertically pass throughthe slot 508 of the circle cleat 500 and be twisted to secure thecomponent to the circle cleat 500.

FIG. 23A shows a bottom surface of an X-Z latch 300 having hourglasskeys 620 and rotatable fasteners 700 attached thereto and extending froman underside of a base of the X-Z latch 300. The hourglass keys 620 andthe rotatably fasteners 700 are configured to engage with an hourglasscleat 520 to secure the X-Z latch 300 to the hourglass cleat 520. Anexample embodiment of an hourglass cleat 520 is shown in FIG. 23B. Thehourglass cleat 520 has a base 502 with mounting hole(s) 503 formedthrough a thickness of the base 502 to secure the hourglass cleat 520 tothe cargo hold floor 4 using fasteners passing through the mountinghole(s) 503. In some embodiments, alignment features may be formed in aback side of the base 502 to aid in installation of the hourglass cleat520 to the cargo hold floor 4. The hourglass cleat 520 has side walls504 extending away from the base 502 out of the X-Y plane and connectingwith flanges 506, the height of the side walls 504 defining a thicknessof the slot 508 oriented along the length of the hourglass cleat 520 inthe X-direction. The flanges 506 and the slot 508 are shaped to formhourglass insets 525 (see also, FIG. 24D) that are configured to ensureproper alignment of, and engagement with, a component having hourglasskeys 620 on a bottom surface thereof. The rotary fasteners 700 of acomponent are configured to vertically pass through the slot 508 of thehourglass cleat 520 and be twisted to secure the component to thehourglass cleat 520.

It is advantageous for the shapes and sizes of the respective keys andinsets to be mutually exclusive, such that, for example, a circle keycannot fit within a square inset, a triangle inset, or an hourglassinset; a square key cannot fit within a circle inset, a triangle inset,or an hourglass inset; a triangle key cannot fit within a circle inset,a square inset, or an hourglass inset; and an hourglass key cannot fitwithin a circle inset, a square inset, or a triangle inset.

A method of installing components of a cargo management system isdisclosed herein, the method comprising: forming and/or providing insetshaving a first shape in an upper surface of a first subset of aplurality of cleats; forming and/or providing insets having a secondshape in an upper surface of a second subset of the plurality of cleats;rigidly attaching a plurality of cleats to a floor of the cargo hold;attaching keys and rotatable fasteners to the components of the cargomanagement system, a first subset of the keys having the first shape anda second subset of the keys having the second shape; engaging the firstsubset of keys with the first subset of cleats; engaging the secondsubset of keys with the second subset of cleats; and rotating therotatable fasteners are configured to secure the components of the cargomanagement system to a respective cleat against which the rotaryfastener is engaged. In some embodiments of the method, the first andsecond shapes are different shapes. In some embodiments of the method,the first and second shapes comprise geometric or amorphous shapes. Insome embodiments of the method, the geometric shapes comprise one ormore of a square, a triangle, a circle, a hexagon, a pentagon, and anhourglass. In some embodiments of the method, each cleat comprises aback, through which each cleat is rigidly attached to the cargo holdfloor 4, at least two side walls on opposing lateral sides of the back,and a top surface, against which the rotatable fasteners are tightenedto secure the components of the cargo management system to the cleat. Insome embodiments of the method, at least one cleat has at least twoinsets formed through a thickness of the upper surface, into which acorresponding one of the keys can be inserted during installation of thecomponents of the cargo management system. In some embodiments of themethod, at least one cleat has a slot formed through a thickness of theupper surface, the slot being continuous and uninterrupted along alength of the cleat to bifurcate the upper surface of the cleat, therebydefining at least two flanges in the cleat. In some embodiments, themethod comprises inserting the rotatable fasteners through the slot toengage with an internal surface of the at least two flanges. In someembodiments, the method comprises progressively tightening the flangesbetween the rotatable fastener and the component of the cargo managementsystem to which the tightener is attached by rotating the tightener in afirst direction. In some embodiments of the method, a width of therotatable fasteners is less than a distance between the side walls ofthe cleat.

FIGS. 25 through 30 show various aspects of a Y-Z latch, generallydesignated 400, according to an example embodiment. As shown in FIG. 25,a base plate 410 is rigidly connected to the lateral sides 5 of thecargo hold. The base plate 410 has a latch head slot 424, which isconfigured to have a latch head 430 removably attached thereto, and/or aroller assembly slot 422, which is configured to have a roller assembly480 removably attached thereto. The base plate 410 has an auxiliary slot416 formed therein, which can be used to secure further features to thebase plate 410.

The latch head 430 has a lateral (e.g., Y-direction) stop surface 450and a vertical (e.g., Z-direction) stop surface 440. The latch head 430is configured to prevent lateral and vertical movement of the cargo unitwithin the cargo hold while allowing movement of the cargo unit in theX-direction along the length of the aircraft. The latch head 430 has alatch toe 432 that engages, as shown in FIG. 26, against a base-latchheel 412 formed in the base plate 410. The latch head 430 is securedwithin the latch head slot 422 to the base plate 410 by a pull pin 420.To provide support against movement of the latch head 430 relative tothe base plate 410 in the X-direction, the base plate 410 has aprotuberance 423 formed thereon, over which the latch head 430 issecured, by a cavity corresponding in size and position to that of theprotuberance 423, by the pull pin 420 The base plate 410 has athrough-hole 421 extending through the protuberance 423 in theX-direction, and the latch head 430 has a passage 434 that, when thelatch head 430 is fully installed over the base plate 410, thethrough-hole 421 and the passage 434 are substantially coaxiallyaligned, within a manufacturing tolerance, and can be rigidly securedtogether by inserting the pull pin 420 through a first portion of thepassage 434, through the through-hole 421, and through a second portionof the passage 434, as shown in the example embodiment of FIGS. 25-30.

The roller assembly 480 comprises a roller 490 rotatably attached to aframe 482 of the roller assembly 480 to provide vertical support (e.g.,in the Z-direction) to the cargo unit and substantially frictionlessmotion of the cargo unit in the X-direction along the length of thecargo hold. The roller assembly 480 has keyed alignment features thatensure that the roller assembly 480 cannot move relative to the baseplate 410 in the X-direction. Among these alignment features are aroller toe 484 which is secured to the base plate 410 by a base-rollerheel 414 formed in the base plate 410; a rib 428 formed along the lengthof the roller assembly slot 422 of the base plate 410 and acorresponding recess in the bottom surface of the roller assembly 480,which are both oriented so as to be substantially coplanar wheninstalled together, extending in the Y-Z plane, substantiallyperpendicular to the X-direction; and lateral tabs 486 spaced apart onopposite sides of the roller assembly 480 in the X-direction, which fitinto slots 426 formed on opposite sides of the base plate 410 in theX-direction. The lateral tabs 486 comprise protrusions that areconfigured to fit within a keyed portion of the slots 426 such that,when the roller assembly 480 is not fully engaged over the base plate410, the lateral tabs 486 protrude from the roller assembly 480 in theX-direction and serve as a visual indicator that the roller assembly 480is not fully engaged with the base plate 410. Furthermore, theengagement of the lateral tabs 486 into the keyed portion of the slots426 of the base plate 410 provides a retention force to prevent theroller assembly 480 from separating from the base plate 410 in theZ-direction due to normal maneuvers of the aircraft in configurations ofthe cargo hold where the Y-Z latch is not engaged with a cargo unit. Thebase plate 410 has a plurality of mounting holes 418 formed through athickness thereof for rigidly attaching the base plate 410 to the innersurface of the cargo hold.

FIG. 29 shows an example embodiment of a second configuration of the Y-Zlatch 400, in which the roller assembly (480, FIGS. 25-28) is omitted inembodiments of a cargo management system that incorporates fixed rollers800 rigidly attached to the cargo hold floor 4. FIG. 30 shows anexploded view of the Y-Z latch according to the embodiment shown in FIG.29.

FIGS. 31A and 31B illustrate how the roller assembly 480 and the latchhead 430 can be attached to the base plate 410. The roller toe 484 ofthe roller assembly 480 is inserted against the base-roller heel 414 andthe roller assembly 480 is then pivoted in the clockwise direction intothe roller assembly slot 422 of the base plate 410, as shown in FIG.31A, such that the roller-base alignment features (426, 428, 486) engagewith each other to retain the roller assembly 480 against the base plate410. The latch toe 432 of the latch head 430 is inserted against thebase-latch heel 412 and the latch head 430 is then pivoted in thecounterclockwise direction into the latch head slot 424 of the baseplate 410, as shown in FIG. 31B, such that the pull pin 420 can beinserted through the through-hole 421 of the base plate 410 and thepassage 434 of the latch head 430 to secure the latch head 430 to thebase plate 410.

As such, a method of assembling a Y-Z latch is disclosed. According toone embodiment, the method comprises attaching the base plate within thecargo hold of an aircraft, attaching the latch head to the base plate,and, optionally, attaching the roller assembly to the base plate. Insome embodiments, attaching the latch head comprises engaging the latchtoe against the base-latch heel of the base plate and pivoting the latchhead down against the base plate, over the latch-base mounting feature(e.g., a protuberance extending from the base plate), and inserting thepull pin through a hole formed through the latch-base alignment featureand a through-hole formed through the latch head in the X-direction. Insome embodiments, the latch-base alignment feature is configured toprevent a movement of the latch head relative to the base plate in theX-direction and the Y-direction. In some embodiments, the pull pin has acollar that is lockingly inserted around a narrowed portion to preventremoval of the pull pin without first removing the collar in a directionorthogonal to the direction of removal of the pull pin. In someembodiments, attaching the roller assembly to the base plate comprisesengaging the roller toe against the base-roller heel of the base plateand pivoting the latch head down against the base plate, over theroller-base alignment features, such that the lateral tabs are locatedwithin a slot formed in the base plate. In some embodiments, theroller-base alignment features comprise a rib of the base plate and acorresponding recess in the bottom surface of the roller assembly, therib and the recess being defined in the Y-Z plane, and the lateral tabsand keyed portion of the slots in the base plate. In some embodiments,the roller-base alignment features prevent motion of the roller assemblyin at least the X-direction relative to the base plate. In someembodiments, the roller allows a motion of the cargo unit over/throughthe Y-Z latch in a substantially frictionless manner.

It is understood that the example embodiments disclosed herein are notlimiting and do not restrict the object disclosed herein. In particular,it will be evident to the person skilled in the art that the featuresdescribed herein may be combined with each other arbitrarily, and/orvarious features may be omitted therefrom, without any resultantdevices, systems, and/or methods deviating from the subject matterdisclosed herein.

While at least one example embodiment of the present invention(s) isdisclosed herein, it should be understood that modifications,substitutions and alternatives may be apparent to one of ordinary skillin the art and can be made without departing from the scope of thisdisclosure. This disclosure is intended to cover any adaptations orvariations of the example embodiment(s). In addition, in thisdisclosure, the terms “comprise” or “comprising” do not exclude otherelements or steps, the terms “a”, “an” or “one” do not exclude a pluralnumber, and the term “or” means either or both. Furthermore,characteristics or steps which have been described may also be used incombination with other characteristics or steps and in any order unlessthe disclosure or context suggests otherwise.

1. A system for ensuring proper installation of components of a cargomanagement system within a cargo hold, the system comprising: aplurality of cleats rigidly attached to a floor of the cargo hold; afirst subset of the plurality of cleats comprising insets having a firstshape; a second subset of the plurality of cleats comprising insetshaving a second shape; keys and rotatable fasteners attached to thecomponents of the cargo management system, a first subset of the keyshaving the first shape and a second subset of the keys having the secondshape; wherein the first subset of keys can only engage with the firstsubset of cleats and the second subset of keys can only engage with thesecond subset of cleats, and wherein the rotatable fasteners areconfigured for rotary movement to secure the components of the cargomanagement system to a respective cleat, against which the rotaryfastener is engaged.
 2. The system of claim 1, wherein the first andsecond shapes are different shapes.
 3. The system of claim 2, whereinthe first and second shapes comprise geometric or amorphous shapes. 4.The system of claim 3, wherein the geometric shapes comprise one or moreof a square, a triangle, a circle, a hexagon, a pentagon, and anhourglass.
 5. The system of claim 1, wherein each of the cleatscomprises a back, through which each cleat is rigidly attached to thecargo hold floor, at least two side walls on opposing lateral sides ofthe back, and a top surface, against which the rotatable fasteners aretightened to secure the components of the cargo management system to thecleat.
 6. The system of claim 5, wherein at least one cleat has at leasttwo insets formed through a thickness of the upper surface, into which acorresponding one of the keys can be inserted during installation of thecomponents of the cargo management system.
 7. The system of claim 5,wherein at least one cleat has a slot formed through a thickness of theupper surface, the slot being continuous and uninterrupted along alength of the cleat to bifurcate the upper surface of the cleat, therebydefining at least two flanges in the cleat.
 8. The system of claim 7,wherein the rotatable fasteners are configured for insertion through theslot and to engage with an internal surface of the at least two flanges.9. The system of claim 8, comprising a tightener for each rotatablefastener, wherein the tightener is configured to clamp the flangesbetween the rotatable fastener and the component of the cargo managementsystem to which the tightener is attached progressively tighter due to arotary movement of the tightener.
 10. The system of claim 8, wherein awidth of the rotatable fasteners is less than a distance between theside walls of the cleat.
 11. A method of installing components of acargo management system within a cargo hold, the method comprising:providing insets having a first shape in an upper surface of a firstsubset of a plurality of cleats; providing insets having a second shapein an upper surface of a second subset of the plurality of cleats;rigidly attaching a plurality of cleats to a floor of the cargo hold;attaching keys and rotatable fasteners to the components of the cargomanagement system, a first subset of the keys having the first shape anda second subset of the keys having the second shape; engaging the firstsubset of keys with the first subset of cleats; engaging the secondsubset of keys with the second subset of cleats; and rotating therotatable fasteners configured to secure the components of the cargomanagement system to a respective cleat, against which the rotaryfastener is engaged.
 12. The method of claim 11, wherein the first andsecond shapes are different shapes.
 13. The method of claim 12, whereinthe first and second shapes comprise geometric or amorphous shapes. 14.The method of claim 13, wherein the geometric shapes comprise one ormore of a square, a triangle, a circle, a hexagon, a pentagon, and anhourglass.
 15. The method according to claim 11, wherein each cleatcomprises a back, through which each cleat is rigidly attached to thecargo hold floor, at least two side walls on opposing lateral sides ofthe back, and a top surface, against which the rotatable fasteners aretightened to secure the components of the cargo management system to thecleat.
 16. The method of claim 15, wherein at least one cleat has atleast two insets formed through a thickness of the upper surface, intowhich a corresponding one of the keys can be inserted duringinstallation of the components of the cargo management system.
 17. Themethod of claim 15, wherein at least one cleat has a slot formed througha thickness of the upper surface, the slot being continuous anduninterrupted along a length of the cleat to bifurcate the upper surfaceof the cleat, thereby defining at least two flanges in the cleat. 18.The method of claim 17, comprising inserting the rotatable fastenersthrough the slot to engage with an internal surface of the at least twoflanges.
 19. The method of claim 18, comprising progressively tighteningthe flanges between the rotatable fastener and the component of thecargo management system to which the tightener is attached by rotatingthe tightener in a first direction.
 20. The method of claim 18, whereina width of the rotatable fasteners is less than a distance between theside walls of the cleat.